NASA USLI Rocket Competition
Kolton Jones, Daniel Jones, Timothy Bucklew, Owen Gaul
Mariel Shumate, Keith Andrew
Physics and Astronomy
Western Kentucky University
National Collegiate Competition to launch and return safely a rocket with a
NASA payload to a height of 1 mile.
1. Engage students of all levels in science
a. University
b. High School
c. Middle School
2. National Recruitment
3. PR for NASA and STEM
May 2012- April 2013 NASA Student Launch Teams (University/College)
1. Alabama A&M University -- Normal, Ala.
2. California Polytechnic Pomona -- Pomona, Calif.
3. Century College -- White Bear Lake, Minn.
4. Citrus College -- Glendora, Calif.
5. Clark College -- Vancouver, Wash.
6. Florida A&M University -- Tallahassee, Fla.
7. Georgia Institute of Technology -- Atlanta, Ga.
8. Harper College -- Palatine, Ill.
9. Massachusetts Institute of Technology -- Cambridge, Mass.
10. Mississippi State University -- Starkville, Miss.
11. New Mexico State University -- Las Cruces, N.M.
12. North Carolina State University -- Raleigh, N.C.
13. Northwest Indian College -- Bellingham, Wash.
14. Northwestern University -- Evanston, Ill.
15. Pennsylvania State University -- University Park, Pa.
16. Purdue University -- West Lafayette, Ind.
17. Santa Fe College -- Gainesville, Fla.
18. Tarleton State University -- Stephenville, Texas
19. University of Alabama -- Tuscaloosa, Ala.
20. University of Alabama in Huntsville -- Huntsville, Ala.
21. University of California Davis -- Davis, Calif.
22. University of Central Florida -- Orlando, Fla.
23. University of Florida -- Gainesville, Fla.
24. University of Illinois Urbana Champaign -- Champaign, Ill.
25. University of Louisville -- Louisville, Ky.
26. University of Minnesota -- Minneapolis, Minn.
27. University of Nebraska -- Lincoln, Neb.
28. University of New Hampshire -- Durham, N.H.
29. University of North Carolina Charlotte -- Charlotte, N.C.
30. University of North Dakota -- Grand Forks, N.D.
31. University of Notre Dame -- South Bend, Ind.
32. University of South Alabama -- Mobile, Ala.
33. Vanderbilt University -- Nashville, Tenn.
34. Virginia Tech -- Blacksburg, Va.
35. Western Kentucky University -- Bowling Green, Ky.
36. Windward Community College -- Kaneohe, Hawaii
Student Members of WKU USLI Rocket Team
Vette City Rockets
Name
1 Bucklew, Timothy
2 Carvalho Pelossi,
Bruno
3 Covetts, James
Major
Graduating Class
BS: Mechanical
Engineering
Physics
2014
BS: Computer Science
Brazilian Exchange
Student
2013
4 Dong, Samuel
BS: Computer Science,
BS: Physics
Gatton 2013
5 Dowell, Steven
2014
7 Gaulle, Owen
BS: Electrical
Engineering
BS: Mechanical
Engineering
BS: Physics
8 Ghanta, Akhil
BS: Physics
Gatton 2013
9 Heintzman, Eli
BS: Physics
2015
10 Jones, Daniel
BS: Physics
2013
11 Jones, Kolton
BS: Physics
2014
12 Leszczewicz, Jason
BS: Physics
2013
13 Masuda, Shane
BS: Physics
Gatton 2013
14 Shumate, Mariel
BS: Mechanical
Engineering
BS: Mechanical
Engineering
BS: Physics, BS:
Mathematics
BS: Physics, BA:
French
2014
6 Edens, Jordan
15 Stansel, Jeffrey
16 Wei, Daniel
17 Wood, Duncan
2015
2013
2014
Gatton 2014
Gatton 2013
WKU Vette City Rocket Plans
1.
2.
3.
4.
5.
6.
Design, Budget, Outreach and Testing
Subscale Testing at WKU Rudolf Field: 6 launches, try for 1500 ft
Half Scale Testing at Cemetery Field: 3 Launches, try for ½ mile: 2640 ft
Charge Subscale Testing at E-Field: 1 Launch
Full Scale Test at C-Field: 1 Launch – 1mile
Huntsville Launch in April: 1 Launch – 1mile
11 Month Project
Current: 43.5 lbs, 7.25 ft, 8.0” diameter
NASA Check in every two months
Budget: Max. Rocket and Payload $5k
Cost of full scale engine: $350
Motor Choice: Aerotech L1420R
Students must do 100% of work
Licensed Engine Mentor: Level 3 NAR D. Hanks
Team Name: Vette City Rocket
Mailing Address: 1906 College Heights #11077
Name of Mentor: Darryl Hanks Level 3 NAR certification
NASA words of advice: please make a stable rocket.
WKU Vette City Sponsors
Computer Coding Solutions
Games to Web Design
Nashville Road
Bowling Green, KY
NASA KY Space Grant
UK, EPSCoR
ACE Electrical Engineering
Microprocessors, Boards, PCs
Randolph, Hale & Meredith, Inc.
Industrial Suppliers: Medical, Mechanical,
Display
319 State Street / P.O. Box 1217
Bowling Green, KY. 42101
Phone (270) 781-1462 Fax (270) 781-1524
General Motors
Corvettes in BG
Web Site: www.randolphelectronic.com
E-Mail: sales@randolphelectronic.co
m
Design and Distribution of Microchips
Corporate Headquarters
Microchip Technology Inc.
2355 West Chandler Blvd.
Chandler, Arizona, USA 85224-6199
(480) 792-7200
Creating Robotic Solutions
Interface, applications, controllers
search
• Robotic Designs
•
•Controller Boards
•
•Software and Interface
•
•Chassis and Accessories
•
•Application Studio
•
Customer Service Assistance:
•
 

r

d
A
r
dm





rcp 

rcm  rcg 
d
A

 dm
Dynamic Stability: CP is below CG
SHM about CG due to torques acting at CP damped harmonic motion
Drift Field Parameters
Consider a rocket in open parachute recovery mode at altitude h,
with descent velocity v in the presence of a horizontal wind. The rocket
will drift a distance d from the location of parachute opening. To find the drift
distance we will:
Scale model test launch
at WKU Rudolph Field
1. Use Newton’s Laws of motion to relate the drag force to the weight
and terminal speed of the rocket
2. Estimate the drag force in terms of the drag coefficient and parachute area
3. Determine the descent velocity given the parachute area at terminal speed
4. Relate this to the total time of descent
5. Model various drift distances for a given horizontal wind speed
6. Fit parameters and estimates from flight data
7. Develop a rapid calculation rule consistent with the detailed analysis
Newton’s Second Law of Motion
Descent Velocity During Recovery
Viscous Drag Force : Fd 
 (T )Cd A v 2
2




Dynamical Eq. Newton II :  F j  Fd  W  ma
y
F-drag
g=9.8m/s2
j

 (T )Cd A v 2
Terminal Velocity a  0 : Fd 
 mg  W
2
kg
m3
1.5  Cd  1.9
 air  1.229
A  Arocket  Achute  0.07m 2  0.28m 2  0.35m 2
Small safe recovery v~2.5 m/s
Larger rocket, higher h, v~ 5 m/s
Typical Drag Forces:
12.54 N < F < 18.5 N
x
W=mg
SkyAngle CERT 3 Drogue
Tested Load Capacity (lb)
60.0-129.8
Surface Area (sq.ft)
129
Tested Cd
2.92
Suspension Line Length (inches)
120
Net Weight (oz.)
64
v
2mg
 Cd A
Frictional Drag Force in a Fluid
Humidity and Altitude
Fd 
 (T )Cd A v 2
2
 P   P
 P M PM
 humid (T )   dry    vapor   d d v v
RT
 RdryT   RvaporT 
kg
 humid : density of humid air : 3
m
N
Pd : partial pressure of dry air : Pa  2
m
J
Rd  287.058
: specific gas constant for dry air
kgK
T : temperatur e K
kg
m3
W  mg  Vg
 0  1.22
Pv : partial pressue of water vap or : Pa
R v  461.495
J
specific gas constant for water vapor
kgK
Pv  Psat : Pa
7.5 T
Psat  0.061078 x10
Pa : saturation vapor pressure
Pd  Pabsolute  Pv
density :  (T )    jT j   o  1T
j
Po  101.325 kPa : sea  level
To  288.15 K : sea  level
L  0.0065 K / m : Lapse
J
: ideal
molK
kg
M  0.0289644
: molar mass of air
mol
PM

RT
R  8.31447
 : realtive humidity
T  273.3 
 Lh 

P  Po 1 
T
o 

T  To  Lh
gM
RL
Terminal Velocity and Parachute Area
F  Fd  W  ma  0
Fd 
Cd Av 2
 mg  W
2
2
2mg

d
2
A


r

2
 Cd v
4
SkyAngle 60" Recon drogue chute
Tested load capacity (lb)
Surface Area (sq.ft)
Tested CD
Suspension Line length (in)
Net weight (oz.)
10.2 to 22.1
39.2
1.89
60
18.2
v  3  5 m / s
Cd  0.75 flat  sheet
Cd  1.5  1.8 dome  shaped
kg
  1.22 3
m
60"  D  drogue
Scale Model Parachute for Launch
Brown Cemetery Lane Field
Younger's Creek 583
Descent Velocity and Time
F  Fd  W  ma  0
Fd 
Cd Av 2
 mg  W
2
2
2mg

d
2
A


r

2
 Cd v
4
v
Balloon Borne Sonde
Wind Speed Data
2mg
 Cd A
h
t 
v
 Cd Ah 2
2mg
ejection altitude ft
1000
1007
1437
1354
908
894
descent rate mph
10
12
9
10
12
9
descent rate fps
15
18
13.5
15
18
13.5
descent time s
68.2
57.1
99.9
84.2
47.8
60.8
flight duration s
76.6
65.5
109.5
92.5
56.1
69.6
WKU Rudolph Field
Descent Data
Horizontal Drift Distance – Recovery
v
2mg
 Cd A
h
t 
v
 Cd Ah 2
2mg
Ddrift  t vhorizontal wind  vwind
 Cd Ah 2
2mg
Rock-Sim Simulation of Flight
Solid Works Code for Design
and modeling prior to Construction
with avionics Digilent payload
Cesaroni L1395 Subscale Engine
WKU Rudolph Field
Ag Farm: 1500 ft x 3500 ft
6 Launches with Estes C/D Engines
Break 1500 ft altitude
Characteristic Flight Data from Six Launches at Rudolph Field
alpha bar
Beta Prime
Gamma
First Launch
Second
Launch
First Launch
Peak altitude ft
1017
1038
1457
1389
934
956
Top speed mph
205
204
272
258
169
163
Burn time s
2.8
2.8
2.8
2.8
2.8
2.8
Peak a during boost g's
19.9
15.1
14.9
12.6
11.2
11.5
average a g's
3.3
3.3
4.4
4.2
2.7
2.7
coast to apogee sec
5.6
5.6
6.8
5.5
5.5
6
apogee to ejection sec
-0.1
-0.1
-0.5
-0.5
?
-1
ejection altitude ft
1000
1007
1437
1354
908
894
descent rate mph
10
12
9
10
12
9
descent rate fps
15
18
13.5
15
18
13.5
descent time s
68.2
57.1
99.9
84.2
47.8
60.8
flight duration s
76.6
65.5
109.5
92.5
56.1
69.6
Second Launch First Launch
Second
Launch
1457 ft
Estes Rockets with C/D engines
Defined Flight Active Zones
WKU Rudolph Field Launch
3 Subscale Launches: ½ Size: 2515 ft on 1-6-2013
Engine
peak altitude ft
top speed mph
brun time secs
peak accleration g
average a g's
cost to apogee secs
apogee ejection time
ejection altitude
descent rate mph
descent rate fps
descent time
flight time
First Launch
J520 SK
2450
Second Launch
J580 SS
2515
317
1.6
17.7
8.9
10.2
-2.3
2418
47
71
33.2
45
electronics
main chute
failure
failure
Post Flight Scale Model
Recovery System
Third Launch
J 357 Blue Streak
2094
229
1.8
16.3
5.9
7
-0.1
1784
12
18
94
102.8
Scale Model Launch
Brown Cemetery Lane Field
Younger's Creek 583
Smoothing Coupler
For Ejection
In conclusion:
1. Subscale electronic ejection flight success: March 9, 2013
2. Full Scale Test Flight: launch window March 16-31- not today
3. Huntsville Flight: launch window April 19-21